Device indicating the flying attitude of aircraft



Nov. 13, 193

R. TALAFRE El AL 8 DEVICE INDICATING' THE FLYING ATTITUDE OF AIRCRAFT Filed Sept. 6, 1952 2 Sheets-She et 1 Nov. 15; 1934. R. .TALAFRE ET AL DEVICE INDICATING THE FLYING ATTITUDE O F AIRCRAFT Filed Sepi. 6, 1932 2 Sheets-Sheet 2 alga/re and) .Zi'eni' Renaud Patented Nova E3, 2934- I L .t

DEVECE IICATIENG T FLYING ATTITUDE F AJIRQRAF'E Rmi 'llalafr, Paris, and Henri Renault, La Garenne-Colombes, France Application September 6, 1932, Serial No. 631,91tl lln France September 59, 193i 4 claims. (oi. sis-zoo).

This invention relates to a device for indicat- The flying attitude indicator illustrated coming the flying attitude of aircraft that is to say a prises a screen 1, upon which are marked two device whereby a pilot can constantly ascertain fixed indexes 2 and 3, 2 representing a horizontal .the position or flying attitude of the aircraft and 3 a vertical line. When the aeroplane is fly-' 5 without making external observations: Such a ing horizontally along a straight line, the posi- 6U) device for instance enables a pilot to fly quite tions of the image of the silhouette e and of the safely in fog, in clouds or by night. moving index 5 (coinciding in the present case V The device of the present invention is of the with the index 3) are shown in Figure 1.

type comprising indicating members responsive When the machine rises the image of the sillo to longitudinal and lateral inclinations of the airhouette moves to to (Fig. 2). 65

craft and to its turning movements about a ver When the flying machine banks over to the tical axis, said indicators being of the gyroscopic left without turning, the image of the silhouette or other form of mclinometer and. the indications moves to 4b (Fig. 3) ,the moving index 5 coincidproduced being synthesized into one or more ining then with index 3.

dicating means moving with reference to datum When the aeroplane turns while remaining in lines upon an observation screen. a horizontal plane, the moving index moves to Li a device according to the present invention, 50 (Fig. 2) to the left or to the right side of two at least of indications produced by said inthe screen according to t dire tio of t t dicating members are embodied into a single iming or steering movement.

age by an optical device comprising a moving The combination of the three movements to reflecting element controlled one at least of shownin Figs. 2, 3 and a furnishes an image of said indicating members, said reflecting element every pfl the p receiving a beam of light emanating from a suit- Figure 5 show by Way of example, the case of able source of light and incorporating the indian aeroplane which turns to the right at the same cationoi one at least of the other indicating time as it rises. 80 b The device of the present invention permits The image may, for instance, represent the flying under all conditions with the same ease as front cart of the aircraft asit oul appear to if the pilot could see outside in ideal weather, an observer from the rear of the machine. since the pilot needs merely look at the screen 343 Inorder that the invention may be more clearly to ascertain the flying attitude or" his machine as understood, referencewill now be made to the and 170 on ol it. accompanying drawings which show, byway of Th movements of the ge and of the movexample, a preferred device according to the m mg Ind x up the screen a p du d y three vention applied to an aeroplane, and in which: conveniently arranged m m instr m n whlch Figure 1' shows theimage projected upon the comprl 1 90 screen when the aeroplane flying horjzgnfiany 1. A l ngitudinal inclinometer which indicates along t t the posi ion of the longitudinal axis of the aero-' Fl e 2 shows the position taken by the im- Plane W resQectto a horizontal p e; age ai the aeroplane is rising; 2. A lateral mclmometer indicating the posi- 4'0 Figure 3 shows t position of th image when tion of the transversal or cross axis of the flying 95 the aeroplane is banking to the left sidej machine with reference to an horizontal plane;

Figure 4 shows theiposition of the image when and I I e the aeroplane is turning in an horizontal plane; A Steering lndlcator lndlcatlrgg t e move- FiguIe-S shows the position of the image h ments of'the aeroplane about a vertical axis passthe aeroplane turns to the right at the same tim as it rises; plane Fig 6 is a cmSS S-ection f an embodiment of The longitudinal mclmometer comprises esthe complete attitude indicator of the invention sentialiy yr p 6 pended from a Cardan taken along (Fig 7 mountmg in such, a manner that the centre of Fig. 7 isa cross-section of said indicator taken vity of the gyroscope is located slightly below 105 1 7 7 (Fig and the centre of suspension.

Fig. 8 isa cross-section of said indicator taken In this manner, the plane of the gyro pc. along 3-3 (Fig, 5), whether at rest or rotating 1s very nearly hOI'l- In said drawings like partsare indicated 1) zontal and the device assumes a very slow and like reference characters; very small movement of precession,- no

ing through the centre of gravity of the aero- 10o To.the rod 22 c1- rod 23 which constitutes the moving index shown The gyroscope 6 turns in a frame '7 pivoted on an axis a '(parallel to the longitudinal axis of the aeroplane) 'inside a frame 8. The latter may pivot in journals 8a and 8b fixed in the body of the machine and supports a mirror 9.

Referring to Figs. 7 and 8. it will be seen that a. light ray 10 falling upon the centre of the mirror 9 will be reflected at 11 and fall .on the screen If, at this moment, the aeroplane should descend both the light ray 10 and the screen 1 which are carried away by the aeroplane move relatively to the horizontal plane contain n the gyroscope 6 and to the mirror 9 and the reflected ray will fall upon the screen at a point below 12 and will thus indicate by its position that the flying machine is descending.

It can be seen that neither the movements of the aircraft about its longitudinal axis nor its turning movements about a vertical axis have any influence upon the relative positions of the mirror 9 and of the screen 1.

The construction of the transverse inclinometer (Figs. 6 and 7) is similar to that of the longitudinal inclinometer. However, in this case, the journals 14a and 14b of the outer frame 14 are disposed along an axis a1 (11 parallel to the longitudinal axis of the aeroplane. The journals 14a. and 14b are secured to the body of the machine. The outer frame 14 supports a part 15 which may control the rotating movements of a silhouette 16 (Figs. 6 to 8) representing the aeroplane. If a source of light 17 and a suitable optical system are provided, the light beam emanating from said source will conform in shape to the outlines of the silhouette 16 and give of it a real image to the right of said system. It may readily be seen that if the part 15 and the silhouette 16 should turn in the same direction, an image would appear upon this screen which would assume relatively to the horizontal index line 2 (Figs. 1 and 5) inclinations which would be opposite or inverse of those to the aeroplane itself with respect to a horizontal plane. It then the relative directions of rotation of the parts 15 and 16 are reversedthrough a suitable process a. correct displacement of the image 4 will be obtained.

Practically, the longitudinal inclinometer is arranged in such a manner that through the medium of a convenient optical system, the

light rays' coming from the transverse inclinometer, fall upon the mirror 9 (Figs. 7 and 8) so that a combination of both movements isobtained.

The steering or veering indicator (Figs. 6 to 8) consists of a gyroscope 19 suspended in a single moving frame 20 pivoted injournals 20a and 20b (secured to the aeroplane) about an axis 12 a2 parallel to the longitudinal axis of the machine. If the machine steers or veers about a vertical axis passing through its centre of gravity, the 'plan of rotation of the gyroscope 19 which is normally vertical tends to turn about the suspension axis a2 and a2 in a direction which depends upon the direction of rotation of the gyroscope. The frame 20 is rigidly secured to-a rod 21 which forms one side of a parallel joint, the axis of rotation a2. a2 and a3 a3 0! which are fixed with respect to the aeroplane. the parallel joint is secured a.

at 5 (Figs. 4 gyroscope 19- and 5). A spring 24 gives to the a suitable middle position.'

In the embodiment of the complete device shown in Figsffi to 8, a casing 25 contains the three gyroscopes.

Behind this casing is placed an auxiliary casing 26 in which is disposed the apparatus for reversing the relative movements of the lateral inclinometers, thesilhouette 16 of the flying machine and the lighting device. The silhouette is illuminated by any suitable lighting system so arranged as to throw out parallel light rays (Fig. 7). In the embodiment shown in the drawings this lighting system is made of a source of light 17 disposed at the focus of a converging lens 26. The silhouette is, as previously set forth, controlled by the transverse inclinometer, the movement of which is reversed by a suitable device such as pulleys engaged by a cross wire. The light rays then enter the converging lens which gives of the silhouette a real image reflected by a prism or a mirror 28 and then by mirror 9 secured to the longitudinal inclinometer.

The light rays fall finally upon the translucent screen 1 upon whichthey form the luminous image 4 of the silhouette.

The rod 23 moves in front of the screen while remaining parallel to itself. This rod constitutes the moving index 5 of the steering or veering indicator. Opposite to this rod is placed, tor instance, a glass 24 which protects the movin rod against external influences.

The gyroscopes may be driven by any suitable 1 means such as air pressure or an electrical device. By way of example, the necessary power may be furnished by a small air compressor actuated by the air in which the flying machine is travelling. I v

The device according to the present invention offers among others the following advantages;

1. It enables the pilot to control the flying conditions with the aid of only one instrument: 1

2. It gives instantaneous indications;

3. It is much easier to realize the position oi. the flying machine from an image than from' the indications of several instruments which necessitate reading characters. All these instruments may be replaced by the simple device of the present invention, which enables even an untrained or unskilled pilot to control his machine even without external observation.

4. It may be so constructed as tc'ccnstitute a 1. A device for indicating the flying attitude oi aircraft comprising indicating members responsive respectfullyto longitudinal and lateral inclinations o! the aircraft, an observation screen for receiving a beam of light, a suitable source 0! .light, means controlled by one or said indicating members for incorporating the image oi an aircratt into said beam of light, and a moving reflecting element eperatively connected with the other indicating member {or about a fore and aft with I projecting said beam 0! light upon the ebeervc- .59

tion screen to control the position of said image up and down on said screen, whereby the indications of the indicating members are synthesized into the image moving upon said screen in accordance with the lateral and longitudinal inclinasaid indicating members and interposed in saidbeam of light which thereafter conforms in shape to the outlines of said aircraft simulating element, and a moving reflecting element operatively connected with the other indicating member for projecting said beam of light upon theobservation screen, whereby the indications of the indicating members are synthesized into one image moving upon said screen in accordance with the lateral and longitudinal inclinations of the supporting aircraft.

3. A device'for indicating the flying attitude of aircraft comprising'indicating members responsive respectively to longitudinal and lateral inclinations of the aircraft; an observation screen for receiving a beam of light, a suitable source of light, an aircraft simulating elementoperatively connected with the lateral inclination indicatin member and receiving saidbeam of light which conforms in shape to theoutlines of said aircraft simulating element, and a moving reflecting element operatively connected with the longitudinal inclination indicating member for projecting said beam of light upon the observation screen to control the position of said image up'and down on said screen whereby the indications of the lateral and longitudinal inclinations indicating members. are synthesized into one image moving upon said screen in accordance with the lateral and longi-' tudinal inclinations of said supporting aircraft.

4. A device for indicating the flying attitude of aircraft comprising indicating members responsive respectively to longitudinal and lateral inclinations of the aircraft, anobservation screen for receiving a beam of light, a suitable source of light, means controlled about a fore and aft axis by one of said indicating members for incorporating therimage of the aircraft into said beam of light, a moving reflecting element operatively connected with the other indicating member for projecting said beam-of light upon the observation'screen, to control the position of said image up and down on said screen whereby the indications of the indicating members are synthesized into one image moving upon said screen in accordance with the lateral and longitudinal inclinations ofthe supporting aircraft, and a third indicating member responsive to the turning movements of theaircraft about a vertical axis, said indicating member moving upon said screen in front of said image. I

'REMI TALAFRE. HENRI RENAULT. 

